Method of neutralising ground ordnance

ABSTRACT

A method of neutralising ground ordnance, the method comprising: providing a missile device ( 10 ) comprising a longitudinally extending body ( 12 ) defining a fore and an aft region and a casing ( 18 ) which houses an explosive material; penetrating the ground with the missile device in the vicinity of the ground ordnance; and initiating the explosive material. The explosive material is such that initiation of the explosive material avoids sympathetic initiation of the ground ordnance.

The present invention relates to method of neutralising, rendering safe,or at least impairing the performance of ground ordnance. In particular,but not exclusively, the invention relates to a method of neutralising,at least partly excavating, and separating components of improvisedexplosive devices (IEDs).

The use of explosives to target military forces in conflict is known andmines have been used frequently to attack vehicles and dismountedpersonnel. Similarly, IEDs have been used by insurgent and terroristgroups for many years. However, the terms ‘IED’ and ‘mine’ are notsynonymous.

The IED is a device placed or fabricated in an improvised mannerincorporating destructive, lethal, noxious, pyrotechnic or incendiarychemicals and designed to destroy, incapacitate, harass or distract. Itis normally constructed from non-military components, and oftencomprises a number of separate components which are spaced apart. Theinitiator, power supply, main charge and firing switch of an IED areoften packaged separately and thus represent a larger and more complextarget to neutralise. There are many variants of IEDs and they are oftenconstructed to a highly variable build standard.

A mine is an integral explosive munition designed to be placed under, onor near the ground or other surface area and to be actuated by thepresence, proximity or contact of a person, land vehicle, aircraft, orboat. The military mine most often has all of the principal componentspackaged into a single container and is built to a more consistent andhigher build standard.

Therefore, the IED typically represents a greater threat than aconventional mine. More recently, particularly in Iraq and Afghanistan,the IED has become the insurgent weapon of choice and is a major causeof casualties, both to coalition forces and the indigenous population.The techniques and weapons that are employed to render safe mines tendto be wholly inappropriate or ineffective for the rendering safe ofburied IEDs.

Both mines and IEDs are capable of being initiated in a variety of ways.Time initiation uses mechanical, electronic or chemical means of delay.Command initiation uses physical or electronic means of initiating anexplosive charge by remote control. Victim operation relies on some formof stimulus provided by the victim to trigger the explosive charge. Themost simple and effective means of victim operated device is thepressure plate, which can be designed to operate when a minimum specificweight is applied to the plate in order to target a specific category oftarget, for example a single person or a vehicle. The overwhelmingmajority of IEDs that have been encountered in Afghanistan have been ofthe victim operated, simple pressure plate variety.

Most IEDs in Afghanistan are buried in the ground and the principalcomponents of the IED such as the initiator, the main explosive chargeand container, the firing switch and power supply are not normallyvisible. This complicates significantly the task of the ExplosiveOrdnance Disposal (EOD) operator who is required to make the IED safe.The complete burial and camouflaging of the IED components alsoincreases the hazard posed to the EOD operator as he or she may berequired to physically touch the ground and soil that is in closeproximity to highly sensitive IED components. The ground in which IEDstend to be buried in Afghanistan is extremely hard and has a high rockcontent. For most of the year the water content in the soil is very lowand this further enhances the hardness of the ground.

A variety of EOD weapons and systems have been developed to assist EODoperators in the rendering safe of IEDs. Most EOD weapons are designedto operate against IEDs that are on the surface and their performanceagainst buried IEDs is sub optimal. On occasion, the use of conventionalEOD weapons may even make the IED more hazardous to the EOD operator.Another disadvantage of existing EOD weapons is that they seldom renderthe IED safe in a single step and require the EOD operator to makemultiple approaches to the IED. This is contrary to two of the coreprinciples of IED disposal, which are to minimise the time spent at theIED and to minimise the number of approaches made, in order to reducethe overall level of hazard to which the EOD operator is exposed.

EOD operators are also required to conduct IED render safe operations inenvironments where there is a significant likelihood that they, theirteam, and other supporting forces will be attacked by other means byterrorists or insurgents.

It is desirable to provide an apparatus which can be assembledexpeditiously and taken into action in a shorter period of time, such asless than five minutes. It is desirable to provide an apparatus which isman portable and does not require the use of special vehicles to bebrought into action.

It is desirable to provide an apparatus that can be operated to rendersafe ground ordnance using a reduced number of stages, such as a singlestage, thus reducing the time that the operator is required to spend atthe ground ordnance.

It is desirable to provide an apparatus which employs propulsion meanscapable of penetrating hard ground, thus eliminating the need to disturbthe ground immediately adjacent to the ground ordnance or itscomponents.

It is desirable to provide a method which is suitable for use withground ordnance, such as IEDs, which comprise a number of separatecomponents, one or more of which may be spaced apart from each other. Itis desirable to provide an apparatus which employs a warhead componentthat disrupts, separates and then expels ground ordnance components fromthe ground.

It is desirable to provide an apparatus which employs a warheadcomponent that can be varied by the operator so as to achieve aninitiation rather than a disruptive effect on the ground ordnance mainexplosive charge.

It is desirable to provide an apparatus which operates in a ‘fail safemode’.

According to a first aspect of the present invention there is provided amethod of neutralising ground ordnance, the method comprising:

-   -   providing a missile device comprising a longitudinally extending        body defining a fore and an aft region and a casing which houses        an explosive material;    -   penetrating the ground with the missile device in the vicinity        of the ground ordnance; and    -   initiating the explosive material,    -   wherein the explosive material is such that initiation of the        explosive material avoids sympathetic initiation of the ground        ordnance.

Avoiding sympathetic initiation of the ground ordnance so that componentparts of the ground ordnance are disrupted and/or separated and thenexpelled from the ground may be better than trying to destroy thecomponent parts. Attempting to destroy the component parts of the groundordnance may make it difficult to identify the component parts and soalso difficult to confirm that all component parts have been completelydestroyed and/or disabled and the area is safe. The disruption,separation and then expulsion from the ground of the component parts mayallow evidence to be collected to ascertain the type and design of theground ordnance.

Initiating the explosive material may include detonating the explosivematerial. Indeed, the initiation may be a detonation.

The method may include the step of creating linear projectiles.Initiating the explosive material typically facilitates creation of thelinear projectiles. The linear projectiles may be formed from or be partof the casing and may be formed from an external surface of the casing.The casing may be configured with shaping features in the form oflongitudinal grooves that create the linear projectiles when theexplosive material is initiated.

The step of creating the linear projectiles may involve theMisznay-Schardin effect.

Initiating the explosive material may cause the casing to expand alongits radial axis. The linear projectiles created by initiation of theexplosive material may move out along the radial axis.

The linear projectiles may disrupt the ground ordnance. The linearprojectiles may separate component parts of the ground ordnance in theirpath. The linear projectiles may be stopped due to the resistance of theground.

The linear projectiles may move in front of a blast wave generated byinitiation of the explosive material. The blast wave may follow thelinear projectiles. The blast wave may also separate the component partsof the ground ordnance.

Initiation of the explosive material may produce gaseous initiationproducts. The gaseous initiation products may comprise one or more ofcarbon monoxide, carbon dioxide, water vapour nitrogen and oxides ofnitrogen. Production of gaseous initiation products may avoidsympathetic initiation of the ground ordnance.

Rapid expansion of the gaseous initiation products may cause theformation of a crater in the ground and may expel the component parts ofthe ground ordnance from the ground.

The explosive material may comprise a material which is reactive toproduce a high volume of a gas. The explosive material may comprise astrong oxidising material. Using a strong oxidising material which maynot undergo initiation may avoid sympathetic initiation of the groundordnance. The explosive material may comprise a perchlorate, such aspotassium perchlorate or ammonium perchlorate. Using perchlorate mayavoid sympathetic initiation of the ground ordnance.

The explosive material may comprise C4, PE4 or the like. Alternatively,the explosive material may be a low explosive material. Using a lowexplosive material may avoid sympathetic initiation of the groundordnance

The casing may be adapted to house up to 300 g of explosive material,preferably up to 250 g.

The explosive material may be a non-detonating or low explosive type. Amain charge may comprise potassium perchlorate. Initiation of the maincharge may generate the gaseous initiation products.

The volume of gaseous initiation products may be high, that is greaterthan 1 cubic centimetre of gap per 1 gram of explosive employed.

The casing may be filed with the explosive material and/or a means ofinitiation immediately prior to use of the missile device.

The method of neutralising ground ordnance may allow a safe distance tobe maintained between an operator of the missile device and the groundordnance. The safe distance may be greater than 100 metres.

The method of neutralising ground ordnance may include the step oflaunching the missile device towards the ground.

Initiation of the explosive material is typically after the missiledevice has penetrated the ground. Initiation of the explosive materialis typically at a period after the missile device has penetrated theground.

The aft region of the missile device may be moveably coupled to a firstdriving plate for receiving a launching force and transmitting thelaunching force to the longitudinally extending body to propel thelongitudinally extending body towards the ground.

The launching force transmitted to the longitudinally extending body maybe reduced by a force absorbing member operatively interposed betweenthe longitudinally extending body and the first driving plate.

Optional features of the first aspect of the present invention may beincorporated into any of the other aspects of the present invention andvice versa.

According to a second aspect of the present invention there is provideda missile device, the missile device comprising:

-   -   a longitudinally extending body defining a fore and an aft        region and comprising a casing adapted to house an explosive        material,    -   wherein the casing includes one or more shaping features to        assist the formation of projectiles upon initiation of the        explosive material.

The or each shaping feature may be longitudinally orientated so as toproduce longitudinally orientated projectiles.

The shaping feature may comprise a plurality of grooves or slots.Alternatively or in addition, the casing may be formed from at least twomaterials, the first material being more yieldable, brittle orcombustible than the second material.

The explosive material may comprise C4, PE4 or the like. Alternatively,the explosive material may be a low explosive material. The casing maybe adapted to house up to 300 g of explosive material, preferably up to250 g.

The explosive material may be a low explosive material such thatinitiation of the explosive material avoids sympathetic initiation ofthe ground ordnance.

The explosive material may comprise a material which is reactive toproduce a high volume of a gas. The explosive material may comprise astrong oxidising material. The explosive material may comprise aperchlorate, such as potassium perchlorate or ammonium perchlorate.

The missile device may include a first driving plate movably coupled tothe aft region for receiving a launching force and transmitting thelaunching force to the body to propel the body towards a target. Thefirst driving plate may have a first face which is non-normal to thelongitudinal axis.

The missile device may include a force absorbing member operativelyinterposing the body and the first driving plate so as to reduce orlimit the peak value of the launching force transmitted to the body.

The missile device may include a plurality of driving plates arranged inseries in a longitudinal direction. A force absorbing member mayoperatively interpose each adjacent driving plate.

The missile device may include a propulsion device which includes thefirst driving plate. The missile device may include a delay initiatordevice. The missile device may be adapted for neutralising groundordnance.

The missile device may include a nose portion provided at the foreregion of the body. The nose portion may be pointed for penetrating anintercepting material, such as the ground.

The nose portion may be releasably connected to the body. The releasableconnection may comprise one or both of a Morse taper and a push fitconnection.

The nose portion may at least partially define a recess for receiving anexplosive material. The nose portion may be adapted to allow a user tovary the amount of explosive material within the recess.

The missile device may include a delay initiator device. The initiatordevice may be located in the recess and longitudinally extend into thecasing. The initiator device may comprise a shock tube.

The first driving plate may be circular. The first driving plate mayinclude an aperture for receiving the initiator device.

Details are not provided here but optional features from the firstaspect may be optional features of the second aspect and vice versa.

Optional features of the second aspect of the present invention may beincorporated into any of the other aspects of the present invention andvice versa.

According to a third aspect of the present invention there is provided amissile device, the missile device comprising:

-   -   a longitudinally extending body defining a fore and an aft        region;    -   a first driving plate movably coupled to the aft region for        receiving a launching force and transmitting the launching force        to the body to propel the body towards a target; and    -   a force absorbing member operatively interposing the body and        the first driving plate so as to reduce or limit the peak value        of the launching force transmitted to the body.

The missile device may include a plurality of driving plates arranged inseries in a longitudinal direction. A force absorbing member mayoperatively interpose each adjacent driving plate.

One or more of the material properties, arrangement and the geometry ofthe force absorbing member may be selected to produce a predeterminedpeak value, or proportion of the peak value, of the launching forcetransmitted to the body.

The force absorbing member may comprise a resilient member. Theresilient member may be formed from an elastomer. Alternatively, theforce absorbing member may comprise a damper, such as a hydraulicdamper.

The missile device may include a propulsion device which includes thefirst driving plate. The propulsion device may be releasably connectedto the body. The releasable connection may comprise one or both of aMorse taper and a push fit connection.

The propulsion device may include guide means for constraining movementof the first driving plate in all but the longitudinal direction. Theguide means may be adapted to constrain movement of the resilient memberin all but the longitudinal direction.

The body may comprise a casing adapted to house an explosive material.The explosive material may comprise C4, PE4 or the like. The casing maybe adapted to house up to 300 g of explosive material, preferably up to250 g.

Alternatively, the explosive material may be a low explosive material.The explosive material may be a non-detonating material. The explosivematerial may comprise a material which is reactive to produce a highvolume of a gas. The explosive material may comprise a strong oxidisingmaterial. The explosive material may comprise a perchlorate, such aspotassium perchlorate or ammonium perchlorate.

The casing may include a plurality of grooves or slots. The grooves orslots may be longitudinally orientated.

The missile device may include an initiator device. The initiator devicemay be located at the propulsion device and longitudinally extend intothe casing. The initiator device may comprise a shock tube.

The first driving plate may be circular. The first driving plate mayinclude an aperture for receiving the initiator device. This assists toconstrain movement of the first driving plate in all but thelongitudinal direction. The force absorbing member may include anaperture for receiving the initiator device.

The first driving plate may have a first face which is non-normal to thelongitudinal axis. The first face may be the exterior or most aft face.The first face may be conical, having an apex which points in the aftlongitudinal direction. The first face may have an orientation which isbetween 10 and 20 degrees, preferably 15 degrees, to a plane which isnormal to the longitudinal axis. Alternatively, the first face may beconvex.

The propulsion device may be adapted to receive the explosive materialsuch that the material is ‘shaped’ by the first driving plate.Therefore, the explosive material has a surface which is complementaryto the profile of the first face.

The missile device may be adapted for neutralising ground ordnance.

The missile device may include a nose portion provided at the foreregion of the body. The nose portion may be pointed for penetrating anintercepting material, such as the ground.

The nose portion may be releasably connected to the body. The releasableconnection may comprise one or both of a Morse taper and a push fitconnection.

The nose portion may at least partially define a recess for receiving anexplosive material. The nose portion may be adapted to allow a user tovary the amount of explosive material within the recess.

Optional features of the third aspect of the present invention may beincorporated into any of the other aspects of the present invention andvice versa.

According to a fourth aspect of the present invention there is provideda missile device, the missile device comprising:

-   -   a longitudinally extending body defining a fore and an aft        region; and    -   a first driving plate movably coupled to the aft region for        receiving a launching force and transmitting the launching force        to the body to propel the body towards a target,    -   wherein the first driving plate has a first face which is        non-normal to the longitudinal axis.

The first face may be the exterior or most aft face. The first face maybe conical, having an apex which points in the aft longitudinaldirection. The first face may have an orientation which is between 10and 20 degrees, preferably 15 degrees, to a plane which is normal to thelongitudinal axis. Alternatively, the first face may be convex.

The missile device may include a propulsion device which includes thefirst driving plate.

The propulsion device may be adapted for receiving an explosivematerial. The propulsion device may be adapted to receive the explosivematerial such that the material is ‘shaped’ by the first driving plate.

The missile device may include a force absorbing member operativelyinterposing the body and the first driving plate so as to reduce orlimit the peak value of the launching force transmitted to the body.

The missile device may include a plurality of driving plates arranged inseries in a longitudinal direction. A force absorbing member mayoperatively interpose each adjacent driving plate.

One or more of the material properties, arrangement and the geometry ofthe force absorbing member may be selected to produce a predeterminedpeak value, or proportion of the peak value, of the launching forcetransmitted to the body.

The body may comprise a casing adapted to house an explosive material.The casing may include a plurality of grooves or slots. The grooves orslots may be longitudinally orientated.

The missile device may include an initiator device. The initiator devicemay be located in the recess and longitudinally extend into the casing.The initiator device may comprise a shock tube.

The first driving plate may be circular. The first driving plate mayinclude an aperture for receiving the initiator device.

Optional features of the fourth aspect of the present invention may beincorporated into any of the other aspects of the present invention andvice versa.

According to a fifth aspect of the present invention there is providedan apparatus for neutralising ground ordnance, the apparatus comprising:

-   -   a longitudinally extending body defining a fore and an aft        region and a casing which houses an explosive material;    -   penetrating means to assist the apparatus penetrating the ground        in the vicinity of the ground ordnance; and    -   initiating means for causing initiation of the explosive        material when the apparatus has penetrated the ground in the        vicinity of the ground ordnance,    -   wherein the explosive material comprising a low explosive        material such that initiation of the explosive material avoids        sympathetic initiation of the ground ordnance.

The explosive material may comprise a material which is reactive toproduce a high volume of a gas. The explosive material may comprise astrong oxidising material. The explosive material may comprise aperchlorate, such as potassium perchlorate or ammonium perchlorate.

The ground ordnance may comprise an IED.

The casing may include a plurality of grooves or slots. The grooves orslots may be longitudinally orientated.

The penetrating means may comprise a nose portion provided at the foreregion of the body. The nose portion may be pointed for penetrating theground.

The nose portion may be releasably connected to the body. The releasableconnection may comprise one or both of a Morse taper and a push fitconnection.

The nose portion may at least partially define a recess for receiving anexplosive material. The nose portion may be adapted to allow a user tovary the amount of explosive material within the recess.

The initiating means may comprise a shock tube.

The apparatus may include a propulsion device. The propulsion device mayinclude a first driving plate movably coupled to the aft region forreceiving a launching force and transmitting the launching force to thebody to propel the body towards a target.

The apparatus may include a force absorbing member operativelyinterposing the body and the first driving plate so as to reduce orlimit the peak value of the launching force transmitted to the body.

The apparatus may include a plurality of driving plates arranged inseries in a longitudinal direction. A force absorbing member mayoperatively interpose each adjacent driving plate. The first drivingplate may have a first face which is non-normal to the longitudinalaxis.

Optional features of the fifth aspect of the present invention may beincorporated into any of the other aspects of the present invention andvice versa.

Embodiments of the present invention will now be described, by way ofexample only, with reference to the accompanying drawings in which:

FIG. 1 is a sectional side view of a missile device;

FIG. 2 is a sectional side view of a propulsion device of the missiledevice of FIG. 1;

FIG. 3 is a sectional side view of a body of the missile device of FIG.1;

FIG. 4 is a sectional side view of a nose portion of the missile deviceof FIG. 1;

FIG. 5 a is a diagrammatic side view of the missile device of FIG. 1 atset up;

FIG. 5 b is a diagrammatic side view of the missile device of FIG. 1during launch;

FIG. 6 a is a diagrammatic side view of the missile device of FIG. 1following launch;

FIG. 6 b is a diagrammatic side view of the missile device of FIG. 1during initiation;

FIG. 7 a is a diagrammatic side view of the missile device of FIG. 1following initiation; and

FIG. 7 b is a diagrammatic side view of the missile device of FIG. 1showing the IED components above ground.

FIG. 1 shows a missile device 10 which, in this embodiment, is suitablefor neutralising ground ordnance in the form of an IED 110. The device10 comprises three main structural portions: a body 12 or warheadassembly, a propulsion device 20, and a nose portion 50. The device 10can be fabricated from a variety of materials including one or more ofstainless steel, mild steel, titanium, aluminium and composite material.

The longitudinally extending body 12 defines a fore 14 and an aft 16region. The body 12 also defines a casing 18 adapted to house anexplosive material. The explosive material can be a high explosive, suchas PE4. However, in another embodiment, the material can be a lowexplosive.

A propulsion device 20 is provided at the aft region 16 of the body 12and includes a number of driving plates 30, 32 which are arranged inseries in a longitudinal direction and movably coupled to the aft region16. The plates receive a launching force produced by initiation of theexplosive material 100 and sequentially transmit this launching force tothe body 12 to propel the body 12 towards a target.

A force absorbing member in the form of a resilient plate 34 made from arubber material operatively interposes 34A each adjacent driving plate.This reduces or limits the peak value of the launching force transmittedto the body 12 and so assists to maintain the integrity of the body 12.

The missile device 10 includes an initiator 40. The missile device 10may be initiated electrically or by a shock tube, depending on the typeof initiator employed. The initiator 40 is located at the propulsiondevice 20 and longitudinally extends into the propelling explosivecharge 100. A length of shock tube 42A is embedded in the propellingexplosive charge 100 and this tube runs to a second initiator which is adelay initiator and is embedded in the casing 18. An electrical wire, orshock tube, 42 is connected to the initiator control 44. Activation ofthe initiator control 44 causes initiation of the propelling explosivecharge 100. The initiation of the propelling explosive charge 100 causesthe shock tube 42A to initiate the delay initiator embedded in theexplosive charge in the casing 18.

The driving plates 30, 32 and resilient plates 34 are circular with anaperture for receiving the initiator 40. This provides guide means toconstrain movement of the plates in all but the longitudinal direction.The shock tube is embedded in the bulk explosive within the propulsionhousing 22 such that the initiator 40 can only be initiated by theinitiation of the propelling explosive charge. This prevents the missiledevice 10 from functioning in the event of a failure in the propellingcharge.

The initiator 40 is held in a collar 44, in intimate contact with themain explosive charge, so as to prevent set back during the firing ofthe propulsion charge. A range of initiator delays may be employed butthose in the range of 10 to 100 ms are appropriate for safe use againstlive IED targets. A number of pins 22 can be inserted within aperturesin the collar 44 and then into bores of the propulsion device 20 so thatthey are arranged circumferentially around the driving plates 30, 32 andresilient plates 34. This provides further guide means for constrainingmovement of the plates in all but the longitudinal direction.Alternatively, a plastic cup may be employed to provide bothenvironmental protection and a means of securing the driving plates andthe propelling explosive charge.

The first driving plate 30 has a first or exterior face 34 which isnon-normal to the longitudinal axis. This face 34 is conical, having anapex which points in the aft longitudinal direction and a surfaceorientation which is 15 degrees to a plane which is normal to thelongitudinal axis. The explosive material 100 is packed in contact withthe exterior face 34 of the first driving plate 30 so that the materialis ‘shaped’ by the first driving plate 30. Therefore, the explosivematerial has a surface which is complementary to the profile of thefirst face 34. The user can pack the explosive material 100 immediatelyprior to use and decide upon the amount of material to use.

The shape of the first driving plate 30 is important to achievingreliable performance and the orientation of the exterior face 34 aidsfocussing of the launching force. The driving plates 30, 32 andresilient plates 34 co-operate to reduce the peak force transmitted tothe body 12. These are each sequentially compressed at launch andincrease the time over which the force generated by the propulsionsystem is applied to the body 12. This reduction in the peak forceapplied to the body 12 maintains the structural integrity of the body 12and aids in the penetration of very hard ground.

The missile device 10 includes a nose portion 50 releasably connected tothe fore region of the body 12. The nose portion 50 is pointed forpenetrating the ground. The nose portion 50 defines a recess 52 forreceiving an explosive material and the user can vary the amount ofexplosive material within the recess.

The external surface of the lower section of the body 12 is configuredwith shaping features in the form of longitudinal grooves 24. Thesefacilitate the creation of linear projectiles 120 upon initiation of themain explosive charge. The high pressures generated cause the body 12 toexpand along its radial axis.

The presence of grooves 24 on the outer surface of the warhead assemblyresults in the creation of linear explosively formed projectiles 120 asa result of the Misznay-Schardin effect. These high velocity projectiles120 move out along a radial axis from the warhead assembly and disruptand separate any IED components in their path. Eventually, the fragmentsare stopped due to the resistance of the ground.

The high velocity projectiles 120 initially move in front of the blastwave 122. The blast wave 122 follows the projectiles 120 and causesfurther separation of the IED components. The initiation of the mainexplosive charge also produces a significant volume of gaseousinitiation products, including: carbon monoxide, carbon dioxide, watervapour, nitrogen and various oxides of nitrogen. The rapid expansion ofthese gases causes the formation of a crater and the expulsion of theIED components and the crater material from the ground.

Using a high explosive, it is more likely that there will be sympatheticinitiation of the IED 110. An alternative type of warhead assembly hasbeen developed which does not rely on an initiating explosive to achievethe desired disruptive effect. This non-detonating or low explosivevariant employs a main charge based on potassium perchlorate, which whengiven the appropriate energetic stimulus, generates a high volume ofgas. This warhead assembly is unlikely to sympathetically initiate anIED main charge, but it will separate components and expel them from theground.

The body 12 is a user filled item and is only fitted with explosive andthe means of initiation immediately prior to use. The quantity ofexplosive employed can be varied by the user between 50 and 250 g,depending on the threat and required effect. To improve the speed ofloading and the integrity of filling, the main explosive charge isplaced into a number of plastic cylinders, each slightly less than thewarhead bore diameter. In an alternative embodiment the main explosivecharge is placed into a warhead charge holder which is slightly lessthan the warhead bore diameter.

The propulsion device 20 is slotted and releasably connected to the body12 using both a Morse taper 25 and a push fit connection 26. Also, thenose portion 50 is releasably connected to the body 12 using push fitconnection. The use of a push fit system and Morse taper improves safetyand is quicker to operate when compared to a screw threaded system.

The missile device 10 can therefore be quickly assembled and operated ina short period of time. Also, the device 10 can be used to neutraliseground ordnance in a single stage, reducing the time that the EODoperator is required to spend at the ground ordnance.

The propulsion means used is capable of penetrating hard ground,eliminating the need to disturb the ground immediately adjacent to theground ordnance or its components.

FIG. 5 a shows the missile device 10 set up on a stand 60 and targetedat an area of the ground near to an IED 110 which comprises the IED maincharge 112, power supply 114 and firing switch 116. The EOD operator 120is located a safe distance from the IED 110.

The EOD operator 120 operates the initiator control 44 to launch themissile device 10 towards the ground. The device 10 impacts andpenetrates the ground as shown in FIGS. 5 b and 6 a. In one embodimentthe pins 22 are pivoted outwards by the launching blast and these can beutilised to resist further penetration of the ground when the device 10is at approximately the correct depth.

After the delay, the main explosive material in the body 12 isinitiated, as shown in FIG. 6 b. The blast wave 122 creates and carriesthe longitudinal projectiles 120 radially through the ground. Some ofthese projectiles 120 impact the IED components, as shown in FIG. 7 a,which are disrupted, separated and expelled from the ground by theprojectiles 120 or the blast wave 122, as shown in FIG. 7 b.

Whilst specific embodiments of the present invention have been describedabove, it will be appreciated that departures from the describedembodiments may still fall within the scope of the present invention.

1. A method of neutralising ground ordnance, the method comprising:providing a missile device comprising a longitudinally extending bodydefining a fore and an aft region and a casing which houses an explosivematerial; penetrating the ground with the missile device in the vicinityof the ground ordnance; and initiating the explosive material, whereinthe explosive material is such that initiation of the explosive materialavoids sympathetic initiation of the ground ordnance.
 2. The method asclaimed in claim 1, the method including the step of creating linearprojectiles.
 3. The method as claimed in claim 1, the method includingthe step of creating linear projectiles, wherein the step of initiatingthe explosive material facilitates creation of linear projectiles. 4.The method as claimed in claim 1, the method including the step ofcreating linear projectiles, wherein the linear projectiles are formedfrom the casing.
 5. The method as claimed in claim 1, the methodincluding the step of creating linear projectiles, wherein the casinghas shaping features in the form of longitudinal grooves that create thelinear projectiles when the explosive material is initiated. 6.(canceled)
 7. The method as claimed in claim 1, wherein initiating theexplosive material causes the casing to expand along its radial axis. 8.The method as claimed in claim 1, the method including the step ofcreating linear projectiles, wherein the linear projectiles separatecomponent parts of the ground ordnance in their path.
 9. The method asclaimed in claim 1, the method including the step of creating linearprojectiles wherein the linear projectiles move in front of a blast wavegenerated by the initiation of the explosive material.
 10. The method asclaimed in claim 8, wherein the linear projectiles move in front of ablast wave generated by the initiation of the explosive material,wherein the blast wave separates the component parts of the groundordnance.
 11. The method as claimed in claim 1, wherein initiation ofthe explosive material produces gaseous initiation products comprisingone or more of carbon monoxide, carbon dioxide, water vapour nitrogenand oxides of nitrogen, such that initiation of the explosive materialavoids sympathetic initiation of the ground ordnance.
 12. The method asclaimed in claim 11 wherein rapid expansion of the gaseous initiationproducts causes the formation of a crater in the ground and expelscomponent parts of the ground ordnance from the ground.
 13. The methodas claimed in claim 1, wherein the explosive material comprises a strongoxidising material, such that initiation of the explosive materialavoids sympathetic initiation of the ground ordnance.
 14. The method asclaimed in claim 1, wherein the explosive material comprises aperchlorate, such that initiation of the explosive material avoidssympathetic initiation of the ground ordnance.
 15. (canceled)
 16. Themethod as claimed in claim 1, wherein the explosive material is a lowexplosive material such that initiation of the explosive material avoidssympathetic initiation of the ground ordnance.
 17. (canceled)
 18. Themethod as claimed in claim 1, wherein initiation of the explosivematerial produces gaseous initiation products comprising one or more ofcarbon monoxide, carbon dioxide, water vapour nitrogen and oxides ofnitrogen, and the volume of gaseous initiation products is greater thanor equal to 1 cubic centimetre per gram of explosive material and suchthat initiation of the explosive material avoids sympathetic initiationof the ground ordnance.
 19. The method as claimed in claim 1, whereinthe casing is filed with the explosive material immediately prior to useof the missile device.
 20. (canceled)
 21. The method as claimed in claim1, wherein the method includes the step of launching the missile devicetowards the ground.
 22. The method as claimed in claim 1, wherein thestep of initiating the explosive material is after the step ofpenetrating the ground with the missile device.
 23. The method asclaimed in claim 1, wherein the aft region of the missile device ismoveably coupled to a first driving plate for receiving a launchingforce and transmitting the launching force to the longitudinallyextending body to propel the longitudinally extending body towards theground. 24-29. (canceled)